Saturn AL-34
The Saturn/Lyulka AL-34 was an unbuilt turboshaft/turboprop engine for rotary and fixed-wing aircraft, proposed by the Soviet Union in the early 1990s. In turboprop form, the engine was offered for light aircraft such as the Sukhoi Su-86 eight-passenger business airplane,[1] the Myasishchev M-101T Gzhel business jet,[2] the ROS-Aeroprogress T-101 Grach nine-passenger aircraft,[3] its derivative T-108 Zolotoy Orel nineteen-passenger aircraft,[4] and the Krunichev T-511 "AIST-M".[5] As a turboshaft, the AL-34 was proposed to power the Mil Mi-54[6] and the Kazan Ansat[7] helicopters. The engine was also considered for unconventional aircraft such as the Mil Mi-30L Vintoplan tiltrotor aircraft,[8] and it was to be an auxiliary engine for powering the boundary layer control system and air cushion on the EKIP flying saucer (a flying wing aircraft).[9]
The AL-34 was one of the few engines to use a recuperator to recover and reuse waste heat from combustion.[10]
The engine came in two versions. The AL-34-1 was an engine that produced 550 horsepower (410 kW) in cruise conditions.[2] It weighed 363 pounds (165 kilograms), which included a compact, 88 lb (40 kg) recuperator. The AL-34-2 was a twin-configuration engine producing 1,100 hp (820 kW), weighing about 1,200 lb (540 kg), and using a common gearbox in a single module.[11]
In October 2000, Saturn/Lyulka confirmed that it was still developing the AL-34 engine in the 1,000 to 1,500 hp (750 to 1,120 kW) power range, and it was working with Kawasaki on stationary powerplant applications.[12] The AL-34 would cost 200-240 thousand dollars, and it would require about 22 million dollars to complete development.[13] As late as January 2004, the engine was still being proposed for the T-511 "AIST-M" derivative of the Krunichev T-411 Aist light utility aircraft.[5] However, the AL-34 never entered production.
Specifications
[edit]Data from [10][2] (for AL-34-1 only)
General characteristics
- Type: turboshaft or turboprop with recuperator
- Length: 1.609 m (5.28 ft; 1,609 mm; 63.3 in)
- Diameter: 0.676 m (2.22 ft; 676 mm; 26.6 in)
- Dry weight: 165 kg (363 lb)
Components
Performance
- Maximum power output: Takeoff: 1,000 hp (750 kW); Cruise: 550 hp (410 kW)
- Bypass ratio: 6.15[9]
- Specific fuel consumption: Cruise: 0.348 lb/(hp⋅h) (0.158 kg/(hp⋅h); 0.212 kg/kWh)
References
[edit]Citations
[edit]- ↑ Jerram, Mike (February 1991). "European correspondence". Flying: World's most widely read aviation magazine. Vol. 118, no. 2. pp. 20–21. ISSN 0015-4806.
- 1 2 3 Zrelov, V. A. (2002). Отечественные ГТД. Основные параметры и конструктивные схемы (Часть 1) [Domestic engines. Basic parameters and construction diagrams. (Part 1) Study guide] (PDF) (Report) (in Russian). Samara State Aerospace University. pp. 99–102. ISBN 5-7883-0210-2. OCLC 1020674498.
- 1 2 3 Kolokolnikov, G.; Chevkinov, V. (June 1992). T-101 aircraft highlighted. Russia: Economic and Social Affairs. FBIS report: Central Eurasia (Report). FBIS Report. Vol. FBIS-USR-92-127. Translated by Foreign Broadcast Information Service (FBIS). Grazhdanskaya Aviatsiya (Civil Aviation) (published October 3, 1992). pp. 29–31. hdl:2027/uiug.30112001465522.
- ↑ Kolganov, V.; Sakharov, V. (April 1993). T-108 aircraft production highlighted. Russia: Economic and Social Affairs. FBIS report: Central Eurasia (Report). FBIS Report. Vol. FBIS-USR-93-130. Translated by Foreign Broadcast Information Service (FBIS). Grazhdanskaya Aviatsiya (Civil Aviation) (published October 7, 1993). pp. 55–58. hdl:2027/inu.30000008301206.
- 1 2 Andrianov, Arnold; Polavsky, Yuri (January 19, 2004). "'АИСТ-М' РАСПРАВЛЯЕТ КРЫЛЬЯ" ['AIST-M' spreads wings]. Крылья Родины [Wings of the Motherland] (in Russian). No. 1. pp. 3–7. ISSN 0130-2701.
- ↑ Kozlov, Dmitry (November 17, 2009). Пресс-конференция ОАО 'МВЗ им. М.Л.Миля,' посвященная 100-летию со дня рождения М.Л.Миля [Press conference of OJSC 'Mil Moscow Helicopter Plant' dedicated to the centenary of the birth of M. L. Mil]. AviaPort.ru (in Russian) (published November 20, 2009).
- ↑ Kartashov, V.; Stepanov, A. (2001). Kazan helicopter plant chief designer's report: ANSAT helicopter design features (PDF) (Report). hdl:20.500.11881/1337 – via European Rotorcraft Forum (ERF) Document Repository.
- ↑ Mikheev, Vadim (October 2006). "Проект "винтоплана" Ми-30" [Project of hybrid helicopter-airplane Mi-30] (PDF). промышленность - проект (industry - project). Взлёт: Национальный аэрокосмический журнал [Take-off: National aerospace magazine] (in Russian). No. 22. Translated by Pushkin, Pavel. pp. 18–19. ISSN 1819-1754 – via Nexis Uni.
- 1 2 Dawson, Dorothy (June 29 – July 5, 1994). "Saucerful of secrets". Lifting-Body Craft. Flight International. Vol. 145, no. 4427. pp. 30–31. ISSN 0015-3710. Gale A16143330.
- 1 2 McDonald, Colin F.; Massardo, Aristide F.; Rodgers, Colin; Stone, Aubrey (May 2008). "Recuperated gas turbine aeroengines, part II: Engine design studies following early development testing". Aircraft Engineering and Aerospace Technology. 80 (3): 280–294. doi:10.1108/00022660810873719. ISSN 1748-8842.
- ↑ "Saturn/Lyulka diversifies business to cope with Russian economic crisis". Reshaping Russia's Propulsion Industry. Aviation Week & Space Technology. Vol. 136, no. 13. March 30, 1992. pp. 44–46. ISSN 0005-2175.
- ↑ Nesterov, Victor (October 4, 2000). "ОАО 'А. Люлька-Сатурн' — без прикрас" [OJSC 'A. Lyulka-Saturn' - unvarnished]. Авиапанорама [Aviapanorama] (in Russian). No. 5. ISSN 1726-6173.
- ↑ "Готовы предложения по дальнейшему совершенствованию авиадвигателя Ал-34" [Proposals for further improvement of the Al-34 aircraft engine are ready] (in Russian). Finmarket News Agency. October 13, 2000.
Bibliography
[edit]- Plot of takeoff SFC vs. takeoff shp for shaft engines, Vick, 2013
- Jerram, Mike (May 1992). "European correspondence". Flying: World's most widely read aviation magazine. Vol. 119, no. 5. pp. 42–43. ISSN 0015-4806.